Radio controlled aircraft, remote controller and methods for use therewith

ABSTRACT

A radio controlled (RC) aircraft includes a receiver that is coupled to receive an RF signal from a remote control device, the RF signal containing command data in accordance with a first coordinate system, wherein the first coordinate system is from a perspective of the remote control device. A motion sensing module generates motion data based on the motion of the RC aircraft. A processing module transforms the command data into control data in accordance with a second coordinate system, wherein the second coordinate system is from a perspective of the RC aircraft. A plurality of control devices control the motion of the RC aircraft based on the control data. In an embodiment, a remote control device commands the RC helicopter to substantially a hovering state when no force is applied to each of a plurality of spring-loaded interface devices.

BACKGROUND OF THE INVENTION

1. Technical Field of the Invention

This invention relates generally to radio controlled toys such asairplanes and helicopters.

2. Description of Related Art

Radio controlled toys such as airplanes, boats, cars and helicopters arepopular. Through the use of a remote control, a user can control themotion of the toy. Radio signals from the remote control, containingcommands from the user, are sent to the toy to control the motion of thetoy. Some radio control devices, such as airplanes and helicopters canbe very difficult to control. These devices operate in three-dimensionalspace and can require great skill on the part of the user to operate. Inparticular, the user is required to consider the perspective of anaircraft when operating the remote control. The same commands that wouldmake the aircraft turn right when the aircraft is moving toward theuser, make the aircraft turn left when traveling away from the user.Simpler controls are needed to enable these devices to be operated byusers with less training or skill.

Further limitations and disadvantages of conventional and traditionalapproaches will become apparent to one of ordinary skill in the artthrough comparison of such systems with the present invention.

BRIEF SUMMARY OF THE INVENTION

The present invention is directed to apparatus and methods of operationthat are further described in the following Brief Description of theDrawings, the Detailed Description of the Invention, and the claims.Other features and advantages of the present invention will becomeapparent from the following detailed description of the invention madewith reference to the accompanying drawings.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING(S)

FIG. 1 is a pictorial/block diagram representation of a remote controldevice 100 and radio controlled aircraft 102 in accordance with anembodiment of the present invention.

FIG. 2 is a pictorial/graphical representation that illustrates roll,pitch and yaw from the perspective of radio controlled aircraft 102 inaccordance with an embodiment of the present invention.

FIG. 3 is a pictorial/graphical representation that illustrates ayaw-axis from the perspective of radio controlled aircraft 102 and anangular orientation with respect to a user coordinate system inaccordance with an embodiment of the present invention.

FIG. 4 is a pictorial/graphical representation that illustrates distanceand altitude coordinates of radio controlled aircraft 102 with respectto the user coordinate system in accordance with an embodiment of thepresent invention.

FIG. 5 is a pictorial/graphical representation that further illustratesthe perspective of radio controlled aircraft 102 with respect to theremote control device 100 in accordance with an embodiment of thepresent invention.

FIG. 6 is a schematic block diagram of a remote control device 100 andaircraft 102 in accordance with an embodiment of the present invention.

FIG. 7 is a pictorial representation of a remote control 150 inaccordance with an embodiment of the present invention.

FIG. 8 is a pictorial representation of a radio controlled aircraft 102launching parachutists 166 and 168 in accordance with an embodiment ofthe present invention.

FIG. 9 is a pictorial/block diagram representation of the set-up ofremote control device 100 and radio controlled aircraft 102 inaccordance with an embodiment of the present invention.

FIG. 10 is a flowchart representation of a method in accordance with anembodiment of the present invention.

FIG. 11 is a flowchart representation of a method in accordance with anembodiment of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

FIG. 1 is a pictorial/block diagram representation of a remote controldevice 100 and radio controlled aircraft 102 in accordance with anembodiment of the present invention. In particular, a radio controlled(RC) aircraft 102, such as a helicopter or other aircraft, operates inresponse to command data 104 received from remote control device 100. Inparticular, remote control 104 and/or RC aircraft 102 are configured toprovide an easier operation by the user. While described in terms of theoperation an RC aircraft, other RC devices such as cars and boats canlikewise be implemented in accordance with the present invention.

Several enhancements are presented along with various optional featuresthat will be described in greater detail in conjunction with FIGS. 2-11that follow.

FIG. 2 is a pictorial/graphical representation that illustrates roll,pitch and yaw axes from the perspective of radio controlled aircraft 102in accordance with an embodiment of the present invention. A coordinatesystem is shown that is aligned from the perspective of the aircraft,and in particular from the perspective of an imaginary pilot of the RCaircraft 102. This aircraft coordinate system provides a way to describethe orientation of the RC aircraft 102 in three-dimensional space interms of the angular displacements, roll, pitch and yaw.

In this coordinate system, clockwise rotation about a roll axis, alignedlongitudinally along the length of the aircraft from the front to thetail, is represented by φ₁. When viewed from the back of the RC aircraft102, clockwise rotation corresponds to a positive roll. Further,rotation about a pitch axis, aligned longitudinally from right to leftthrough the center of the cockpit and perpendicular to the roll axis, isrepresented by φ₂. In this coordinate system, forward pitch of theaircraft 102 is positive pitch. The yaw-axis extends vertically throughthe shaft of main rotor 106 with counter-clockwise displacementrepresented by φ₃.

In an embodiment of the present invention, the aircraft 102 includes oneor more controls that allow the aircraft to be rotated by an amount φ₁about the roll axis, an amount φ₂ about the pitch axis and an amount φ₃about the yaw axis. For instance, in an embodiment where RC aircraft 102is implemented as a helicopter, forward and backward tilt of the mainrotor 106 cause, respectively, positive and negative pitch angles φ₂. Inaddition, right and left tilts of the main rotor 106, cause,respectively, positive and negative roll angles φ₁. Further, the netthrust produced by the tail rotor, taking into consideration any torqueinduced by the rotation of main rotor 106, produces a yaw angle φ₃.

In an embodiment of the present invention, command data 104 from theremote control device 100 are generated in a different coordinatesystem, such as a user coordinate system that corresponds to theorientation of the user. This command data 104 can be transformed intocontrol data in the coordinate system of the aircraft so that the RCaircraft 102 can be controlled based on its orientation to the user,rather than the orientation of an imaginary pilot. The generation ofcommand data 104 and the transformation into control data used tocontrol the orientation of the RC aircraft 102 will be discussed furtherin conjunction with FIGS. 5 and 6.

FIG. 3 is a pictorial/graphical representation that illustrates ayaw-axis from the perspective of radio controlled aircraft 102 and anangular orientation with respect to a user coordinate system inaccordance with an embodiment of the present invention. FIG. 4 is apictorial/graphical representation that illustrates distance andaltitude coordinates of radio controlled aircraft 102 with respect tothe user coordinate system in accordance with an embodiment of thepresent invention. In particular, rotation about a yaw-axis is shown inFIG. 3 in the aircraft coordinate system. In this coordinate system, theyaw-axis extends vertically through the shaft of main rotor 106 with acounter-clockwise angular displacement represented by φ₃. In anembodiment where RC aircraft 102 is implemented as a helicopter, a netcounter-clockwise thrust 107 generated by the tail rotor 108 causes apositive deviation in the yaw φ₃. A net clockwise thrust 109 generatedby the tail rotor 108 causes a negative deviation in the yaw φ₃.

The origin 90 indicates the placement of the origin of a user coordinatesystem that corresponds to the perspective of the user. In an embodimentof the present invention, the user coordinate system is a polarcoordinate system. The position of RC aircraft 102 relative to theorigin 90, can be represented by the altitude Z of the aircraft inrelation to the origin 90, the distance R from the aircraft to theorigin 90, and the angular displacement θ of the aircraft. In summary,the position of the RC aircraft 102 in three dimensional space can berepresented in terms of (R, θ, Z) and the orientation of the aircraftcan be represented in terms of (φ₁, φ₂, φ₃).

FIG. 5 is a pictorial/graphical representation that further illustratesthe perspective of radio controlled aircraft 102 with respect to theremote control device 100 in accordance with an embodiment of thepresent invention. In particular, this configuration assumes that theuser of the remote control device would orient the device with changesof θ, in order to face the RC aircraft 102, regardless of its position.In this configuration, if θ=φ₃, pitch-axis commands from the perspectiveof the remote control device 100, represented by ψ₂, and roll-axiscommands from the perspective of the remote control device 100,represented by ψ₁, correspond directly to pitch-axis controls φ₂ androll-axis controls φ₁ of the RC aircraft 102. When however, θ≠φ₃, theimplementation of a pitch-axis command ψ₂, generally requires bothroll-axis and pitch axis controls φ₁, φ₂. Similarly, the implementationof a roll-axis command ψ₁, generally requires also both roll-axis andpitch axis controls φ₁, φ₂.

In an embodiment of the present invention, remote control device 100generates command data 104 that includes orientation commands ψ₁, ψ₂. RCaircraft 102 is capable of determining position parameters such as θ andφ₃ based on motion data generated by on-board motion sensors. RCaircraft 102 transforms the orientation commands ψ₁, ψ₂ into controldata such as roll-axis and pitch axis controls φ₁, φ₂ as follows:

φ₁=ψ₁ cos(φ₃−θ)+ψ₂ sin (φ₃−θ)   (1)

φ₂=ψ₂ cos(φ₃−θ)−ψ₁ sin(φ₃−θ)   (2)

In this fashion, when a user commands the RC aircraft 102 to pitchforward, the RC aircraft will pitch forward from the perspective of theuser, regardless of the actual orientation of the RC aircraft. Inpractice, a command to pitch forward could be implemented with a pitchforward control if the RC aircraft is facing away from the remotecontrol device 100—when the user is oriented directly with the positionof an imaginary pilot. However, other orientations yield other results:

-   -   if the RC aircraft is facing toward the remote control device        100, a command to pitch forward could be implemented with a        pitch backward control;    -   if the RC aircraft is facing perpendicular to the remote control        device 100, a command to pitch forward could be implemented with        either a roll-right control or a roll-left control, depending on        whether θ−φ₃=90° or θ−φ₃=−90°;        In other circumstances, some other combination of both roll-axis        and pitch-axis controls φ₁, φ₂ is required, as set forth in the        equations (1) and (2) above. Using these transformations, a        remote control device 100 can command the RC aircraft 102 from        the perspective of a user, independent of a yaw-orientation of        the RC aircraft. For instance, when a user commands the RC        aircraft 102 to pitch-forward or roll-left (from the user's        perspective), the RC aircraft pitches forward or rolls left,        regardless of the value of θ or φ₃.

In an embodiment of the present invention, RC aircraft 102 responds to alift control L that controls the lift generated by varying either thevelocity or pitch of the main rotor 106 and a yaw-axis control V thatgenerates a positive or negative net thrust from the tail rotor 108.Remote control 100 generates a yaw-velocity command v=dφ₃/dt, andgenerates a lift command l to control the yaw-axis velocity and lift ina convention fashion, for instance L is equal to or proportion to l andV is equal to or proportional to l. Remote control 100 can optionallygenerate additional controls for controlling other control functions aswell as other features of the RC aircraft 102.

FIG. 6 is a schematic block diagram of a remote control device 100 andaircraft 102 in accordance with an embodiment of the present invention.In particular, remote control device 100 includes a user interface 110such as one or more joy-sticks, click-wheels, buttons, dials, switches,levers or other user interface devices that respond to actions of theuser and generate command data 104 in response thereto. Radiotransmitter 112, generates and transmits an RF signal 114 that containsthe command data 104.

RC aircraft 102 includes receiver 120 that is coupled to receive RFsignal 114 from the remote control device 100 and to regenerate thecommand data 104 contained therein. In particular, command data 104 caninclude data that represents commands such as generated includesorientation commands ψ₁, ψ₂ in accordance with a coordinate system froma perspective of the remote control device 100, other command data thatmay or not be not transformed such as V and L, and other command datacorresponding to other function and features.

RC aircraft 102 further includes a motion sensing module 122 thatgenerates motion data 124 based on the motion of the RC aircraft 102. Inan embodiment of the present invention, motion sensing module 122includes one or more axes of accelerometers or gyroscopes or otherdevices that alone, or with further processing by processing module 126,can generate data that represents θ, φ₃, and/or other motion parameterssuch as R, Z, etc., that can be used in transforming the command data104 to control data 128.

Processing module 126, transforms the command data 104 into control data128 in accordance with a coordinate system from a perspective of the RCaircraft. For example, processing module 126 can generate φ₁, φ₂, v andl, based on the command data 104 such as ψ₁, ψ₂, V and L, and motiondata 124 such as θ, φ₃. This control data 128 is provided to a pluralityof control devices 130 such as actuators, control surfaces, gimbals orother controllers that control the motion of RC aircraft 102 aspreviously described. In particular, control devices 130 and/orprocessing module can further include a feedback controller, statecontroller or other control mechanism that controls aircraft to theparticular values of φ₁, φ₂, v and l.

Processing module 126 may be implemented using a shared processingdevice, individual processing devices, or a plurality of processingdevices and may further include memory. Such a processing device may bea microprocessor, micro-controller, digital signal processor,microcomputer, central processing unit, field programmable gate array,programmable logic device, state machine, logic circuitry, analogcircuitry, digital circuitry, and/or any device that manipulates signals(analog and/or digital) based on operational instructions. The memorymay be a single memory device or a plurality of memory devices. Such amemory device may be a read-only memory, random access memory, volatilememory, non-volatile memory, static memory, dynamic memory, flashmemory, and/or any device that stores digital information. Note thatwhen the processing module 126 implements one or more of its functionsvia a state machine, analog circuitry, digital circuitry, and/or logiccircuitry, the memory storing the corresponding operational instructionsis embedded with the circuitry comprising the state machine, analogcircuitry, digital circuitry, and/or logic circuitry.

In an embodiment of the present invention, processing device 126includes a look-up table, or other routine or application or thatgenerates the control data 128 based on command data 104 and motion data124 in accordance with the equations presented in conjunction with FIG.5 or via one or more other transformations.

In a particular embodiment of the present invention, the command data104 includes a mode selection that, based on its value, selects whetheror not the RC aircraft 102 transforms the command data when calculatingthe control data 128. For instance, the command data can include abinary indicator that has one value that represents a traditional modeof operation and another value that transforms command data 104 togenerate control data 128. In this embodiment, the user can select tooperate the RC aircraft 102 in one mode that transforms orientationcommands from the remote control device 100 from the perspective of theremote control device 100 to the perspective of the RC aircraft 102.Further, the user can instead select to operate the RC aircraft 102 in atraditional fashion by generating command data 104 from the perspectiveof the aircraft itself with yaw-axis controls being proportional toyaw-axis commands and pitch-axis controls being proportional topitch-axis commands. In this fashion, a user can select the mode he orshe finds easiest to use. In addition, different users could select tooperate the RC aircraft 102 in different modes.

RC aircraft 102 optionally includes a launch module 132 that responds tolaunch data 134 included in command data 104 to launch an object fromthe RC aircraft 102, such as a parachutist action figure, bomb missileor other toy or object. Launch module 132 can include a magneticcoupling, retractable hook or other releasable coupling that holds andselectively releases one or more object in respond to the launchcommand, either successively, one object at a time in response torepeated transmissions of the launch data from the remote control device100 or based on individual launch data separately identified for eachsuch object.

In one possible implementation of remote control device 100, userinterface 110 includes a plurality of spring-loaded interface devices,where each of the plurality of spring-loaded interface devices has areturn position that is returned to when no force is applied. In thisimplementation, the remote control device 100 commands the RC aircraftto hover or substantially a hover when no force is applied to each ofthe plurality of spring-loaded interface devices. For example, thepitch-axis, roll-axis and lift command interface devices can have aposition, such as a center position they return to. The center positionof the pitch-axis and roll-axis interface devices operate to generatecommand data 104 for the pitch-axis and roll-axis to correspond tohorizontal flight or substantially horizontal flight within anacceptable level of tolerance. The center position of the lift commandinterface device operates to generate a lift command that corresponds toa lift force that equals or substantially equals the weight of the RCaircraft 102. Where the weight of the RC aircraft changes, such as whenobjects are selectively launched or dropped from the aircraft, theprocessing module 126 can determine a current weight for the RC aircraft102 based on whether objects have been dropped, how many objects and/orwhich objects have been dropped, etc.

FIG. 7 is a pictorial representation of a remote control 150 inaccordance with an embodiment of the present invention. In particularremote control 150, such as remote control device 100, includes amantenna 140 for coupling to a receiver, such as receiver 120. Button142, when pressed by a user, generates a clockwise yaw-velocity command.In a similar fashion, button 144, when pressed by a user, generates acounter-clockwise yaw-velocity command. Lift command device includes aspring-loaded lever that generates a lift command corresponding to ahover-state, when in the center position. The lift command can commandan increased lift force when pushed up to raise the RC aircraft 102 anda decreased lift force when pushed down to lower the RC aircraft 102.Two-axis joystick 148 can be displaced in two-dimensions about a centerposition. Upward and downward displacements of the joystick 148correspond to pitch axis commands and right and left displacementscorrespond to roll-axis commands. When the force is removed from thejoystick 148, it returns to a center position that generates commanddata 104 corresponding to horizontal flight.

Remote control 150 further includes a reference button, for setting thereference position of the RC aircraft 102 to aid in the determination ofmotion data 124, as will be described in greater detail in conjunctionwith FIG. 8. An on-off button 154 is included. Mode control button 158is used to select a mode of operation for the remote control. Forinstance, mode control button 158 can operate on a toggle basis to setor reset the mode to either a mode where joystick 148 and lever 146operate to generate traditional command data 104 used to generatecontrols from the perspective of the RC aircraft, or another mode wherecommand data 104 is transformed from the perspective of the remotecontrol 150 to the perspective of the RC aircraft 102. Indicator light159 can be included to indicate the particular mode selected, by aunique color or by being either on or off.

Additional buttons 156 are included for activating other functions andfeatures of RC aircraft 102 such as the generation of launch data 130for one or more objects or to implement other optional features.

FIG. 8 is a pictorial representation of a radio controlled aircraft 102launching parachutists 166 and 168 in accordance with an embodiment ofthe present invention. In this embodiment RC aircraft 102 includes alaunch module 132 that responds to launch data 132 from a remote controldevice 102 to launch a first action FIG. 166, configured as aparachutist, at a first time along trajectory 164. RC aircraft 102launches a second action FIG. 168, also configured as a parachutist, ata subsequent time along trajectory 162.

FIG. 9 is a pictorial/block diagram representation of the set-up ofremote control device 100 and radio controlled aircraft 102 inaccordance with an embodiment of the present invention. In particular,in this mode of operation, motion sensing module 124 generates motiondata 126 based on the relative motion of the RC aircraft 102. The remotecontrol device 100 and RC aircraft 102 establish an initial position ofRC aircraft 102 that can be used by motion sensing module 124 thatserves as an origin or other reference position. For instance, the usercan be instructed to place the RC aircraft 102 on the ground, apredetermined distance, R_(ref) , from the remote control device 100with the tail of the RC aircraft aligned in the direction of remotecontrol device 100 along axis 170. Pressing the reference button, suchas reference button 152, in this position establishes initialconditions: R=R_(ref), θ=0, Z=0, φ₁=0, φ₂=0, and φ₃=0. As the RCaircraft 102 is subsequently moved in operation, the relative motion ofthe RC aircraft, reflected by motion data 124, can be used to determinea position and orientation of the RC aircraft 102 from the originestablished by the position of remote control 100 during setup.

FIG. 10 is a flowchart representation of a method in accordance with anembodiment of the present invention. In particular a method is presentedfor use with one or more features or functions presented in conjunctionwith FIGS. 1-9. In step 400, an RF signal is received from a remotecontrol device, the RF signal containing command data in accordance witha first coordinate system, wherein the first coordinate system is from aperspective of the remote control device. In step 402 motion data isgenerated based on the motion of the RC aircraft. In step 404, thecommand data is transformed into control data in accordance with asecond coordinate system, wherein the second coordinate system is from aperspective of the RC aircraft. In step 406, the motion of the RCaircraft is controlled based on the control data.

In an embodiment of the present invention, the command data includesroll-axis command data and pitch-axis command data, the control dataincludes roll-axis control data, and the motion data includes yaw-axismotion data, and wherein step 404 includes generating the roll-axiscontrol data as a function of the roll-axis command data, pitch-axiscommand data and the yaw-axis motion data. In addition, the command datacan include roll-axis command data and pitch-axis command data, thecontrol data can include pitch-axis control data, and the motion dataincludes yaw-axis motion data, and wherein step 404 includes generatingthe pitch-axis control data as a function of the roll-axis command data,pitch-axis command data and the yaw-axis motion data. The RF signal caninclude mode data, and wherein, when the mode data has a first value,step 404 is selectively bypassed and the control data generated inproportional to the command data.

The command data can include lift command data and the control data caninclude lift control data, wherein step 404 includes generating the liftcontrol data based on a weight of the RC aircraft. The command data caninclude yaw-velocity command data and the control data can includesyaw-velocity control data and wherein step 404 includes generatingyaw-velocity control data as a proportion of the yaw-velocity commanddata.

FIG. 11 is a flowchart representation of a method in accordance with anembodiment of the present invention. In particular a method is presentedfor use with one or more features or functions presented in conjunctionwith FIGS. 1-10 wherein command data includes launch data. In step 410,an object is launched from the RC aircraft in response to the launchdata. In an embodiment of the present invention, the object includes aparachute, parachutist action figure, toy missile or bomb or otherobject.

As may be used herein, the terms “substantially” and “approximately”provides an industry-accepted tolerance for its corresponding termand/or relativity between items. Such an industry-accepted toleranceranges from less than one percent to fifty percent. Such relativitybetween items ranges from a difference of a few percent to order ofmagnitude differences. As may also be used herein, the term(s) “coupledto” and/or “coupling” and/or includes direct coupling between itemsand/or indirect coupling between items via an intervening item (e.g., anitem includes, but is not limited to, a component, an element, acircuit, and/or a module) where, for indirect coupling, the interveningitem does not modify the information of a signal but may adjust itscurrent level, voltage level, and/or power level. As may further be usedherein, inferred coupling (i.e., where one element is coupled to anotherelement by inference) includes direct and indirect coupling between twoitems in the same manner as “coupled to”. As may even further be usedherein, the term “operable to” indicates that an item includes one ormore of power connections, input(s), output(s), etc., to perform one ormore its corresponding functions and may further include inferredcoupling to one or more other items. As may still further be usedherein, the term “associated with”, includes direct and/or indirectcoupling of separate items and/or one item being embedded within anotheritem.

The present invention has also been described above with the aid ofmethod steps illustrating the performance of specified functions andrelationships thereof. The boundaries and sequence of these functionalbuilding blocks and method steps have been arbitrarily defined hereinfor convenience of description. Alternate boundaries and sequences canbe defined so long as the specified functions and relationships areappropriately performed. Any such alternate boundaries or sequences arethus within the scope and spirit of the claimed invention.

The present invention has been described above with the aid offunctional building blocks illustrating the performance of certainsignificant functions. The boundaries of these functional buildingblocks have been arbitrarily defined for convenience of description.Alternate boundaries could be defined as long as the certain significantfunctions are appropriately performed. Similarly, flow diagram blocksmay also have been arbitrarily defined herein to illustrate certainsignificant functionality. To the extent used, the flow diagram blockboundaries and sequence could have been defined otherwise and stillperform the certain significant functionality. Such alternatedefinitions of both functional building blocks and flow diagram blocksand sequences are thus within the scope and spirit of the claimedinvention. One of average skill in the art will also recognize that thefunctional building blocks, and other illustrative blocks, modules andcomponents herein, can be implemented as illustrated or by discretecomponents, application specific integrated circuits, processorsexecuting appropriate software and the like or any combination thereof.

1. A radio controlled (RC) aircraft comprising: a receiver that iscoupled to receive an RF signal from a remote control device, the RFsignal containing command data in accordance with a first coordinatesystem, wherein the first coordinate system is from a perspective of theremote control device; a motion sensing module, that generates motiondata based on the motion of the RC aircraft; a processing module,coupled to the motion sensing module and the receiver, that transformsthe command data into control data, based on the motion data, and inaccordance with a second coordinate system, wherein the secondcoordinate system is from a perspective of the RC aircraft; and aplurality of control devices, coupled to the processing module, thatcontrol the motion of the RC aircraft based on the control data.
 2. TheRC aircraft of claim 1 wherein the command data includes roll-axiscommand data and pitch-axis command data, the control data includesroll-axis control data and wherein the processor generates the roll-axiscontrol data based on the roll-axis command data and pitch-axis commanddata.
 3. The RC aircraft of claim 2 wherein the motion data includesyaw-axis motion data and the processor generates the roll-axis controldata as a function of the roll-axis command data, pitch-axis commanddata and the yaw-axis motion data.
 4. The RC aircraft of claim 1 whereinthe command data includes roll-axis command data and pitch-axis commanddata, the control data includes pitch-axis control data and wherein theprocessor generates the pitch-axis control data based on the roll-axiscommand data and pitch-axis command data.
 5. The RC aircraft of claim 4wherein the motion data includes yaw-axis motion data and the processorgenerates the pitch-axis control data as a function of the roll-axiscommand data, pitch-axis command data and the yaw-axis motion data. 6.The RC aircraft of claim 1 wherein the RF signal includes mode data,wherein the processing module transforms the command data into controldata in accordance with a second coordinate system when the mode datahas a first value, and wherein the processing module generates thecontrol data as proportional to the command data when the mode data hasa second value.
 7. The RC aircraft of claim 1 wherein the command dataincludes lift command data and the control data includes lift controldata and wherein the processing module generates the lift control databased on a weight of the RC aircraft.
 8. The RC aircraft of claim 1wherein the command data includes yaw-velocity command data and thecontrol data includes yaw-velocity control data and wherein theprocessing module generates the yaw-velocity control data asproportional to the yaw-velocity command data.
 9. The RC aircraft ofclaim 1, wherein the command data includes launch data, the RC aircraftfurther comprising: a launch module, coupled to the receiver, thatlaunches an object from the RC aircraft in response to the launch data.10. The RC aircraft of claim 9 wherein the object includes a parachute.11. A method for use with a radio controlled (RC) aircraft, the methodcomprising: receiving an RF signal from a remote control device, the RFsignal containing command data in accordance with a first coordinatesystem, wherein the first coordinate system is from a perspective of theremote control device; generating motion data based on the motion of theRC aircraft; transforming the command data into control data inaccordance with a second coordinate system, wherein the secondcoordinate system is from a perspective of the RC aircraft; andcontrolling the motion of the RC aircraft based on the control data. 12.The method of claim 11 wherein the command data includes roll-axiscommand data and pitch-axis command data, the control data includesroll-axis control data, and the motion data includes yaw-axis motiondata, and wherein transforming the command data includes generating theroll-axis control data as a function of the roll-axis command data,pitch-axis command data and the yaw-axis motion data.
 13. The method ofclaim 11 wherein the command data includes roll-axis command data andpitch-axis command data, the control data includes pitch-axis controldata, and the motion data includes yaw-axis motion data, and whereintransforming the command data includes generating the pitch-axis controldata as a function of the roll-axis command data, pitch-axis commanddata and the yaw-axis motion data.
 14. The method of claim 11 whereinthe RF signal includes mode data, and wherein, when the mode data has afirst value, the step of transforming the command data is selectivelybypassed and the control data generated in proportional to the commanddata.
 15. The method of claim 11 wherein the command data includes liftcommand data and the control data includes lift control data and whereinthe step of transforming the command data includes generating the liftcontrol data based on a weight of the RC aircraft.
 16. The method ofclaim 11 wherein the command data includes yaw-velocity command data andthe control data includes yaw-velocity control data and wherein the stepof transforming the command data includes generating yaw-velocitycontrol data as a proportion of the yaw-velocity command data.
 17. Themethod of claim 11, wherein the command data includes launch data, theRC aircraft further comprising: launching an object from the RC aircraftin response to the launch data.
 18. The method of claim 11 wherein theobject includes a parachute.
 19. A radio controlled (RC) helicoptersystem comprising: an RC helicopter; a remote control device, inwireless communication with the RC helicopter, that includes a pluralityof spring-loaded interface devices, each of the plurality ofspring-loaded interface devices having a return position that isreturned to when no force is applied, wherein the remote control devicecommands the RC helicopter to substantially a hovering state when noforce is applied to each of the plurality of spring-loaded interfacedevices.
 20. The RC helicopter of claim 19 wherein the remote controldevice commands the RC helicopter from the perspective of a user,independent of a yaw-orientation of the RC helicopter.